Aircraft propeller



Nov. 19, 1946. w. 1. JACKSON AIRCRAFT PROPELLER Filed Aug. 26, 1945 Patented Nov. 19, 1946 UNITED STATES PATENT OFFICE j a ".2,411 -,2"11 1 1 H 1 7 I AIRCRAFT PRoPELLER I William I. Jackson, Orange, Calif.

Application August 26, 1943, Serial No. 500,083

2 Claims. 1

My invention relates to a propeller for aircraft such as airplanes, helicopters, dirigibles and the like, and the principal object of my invention is, to provide a propeller which in structure, combines fan blades and a ring or rim having air passageways, in order to develop extremely high pulling or lifting power when rotated at high speed.

A further object of my invention is to provide a propeller of the character referred to, wherein the blades or vanes, in addition to being inclined in cross section, are inclined lengthwise so their inner ends, which are connected to a hub, are positioned forwardly of the outer ends of said blade and the rim or ring to which said outer ends are connected.

Further objects of my invention are, to construct the propeller in a single piece, by casting methods or otherwise, and to embed in the periphery of the rim or ring portion of the propeller, a member such as a steel cable, in order to counteract and resist bursting strains when thep-ropeller is rotated at high speeds.

With the foregoing and other objects in View, my invention consists of certain novel features of construction and arrangement of parts, which will be hereinafter more fully described and claimed and illustrated in the accompanying drawing, in which;

Fig. 1 is a front elevation of the propeller.

Fig. 2 is a plan view. 1

Fig. 3 is an enlarged cross section taken on the line 3-3 of Fig. 1.

Formed integral with and projecting inwardly from rim I2, midway between its front and rear edges, is a web or flange I3 and the outer ends of blades H are formed integral with this web and with rim I2 by means of outer walls I 4, which connect the outer ends of said blades with said rim and inner walls I5 which connect the blades, inwardly from walls I4, with the inner portion of web I3.

These walls I4 and I5 are disposed transversely of the blades II and formed through web I3 between said walls, and beneath the outer end of each blade is an air passageway such as IS.

Formed through Web between the openings Iii are similar openings to provide air passageways I7, and overlying each of said passageways is an integral plate or wall I8, which is inclined lengthwise to correspond with the transverse inclination of the blades II.

Connecting the inside edges of the inclined plates I8 with web I5 along the inner edges of the openings I1 are integral walls I9, and the outer edges of said inclined plates are integrally connected to the inner face of rim I2 (see Fig. 5).

During operation the propeller is rotated at high speed, and those portions of the blades inwardly from the rim will function in the usual manner and force a heavy column of air rearwardly through the rim or ring. At the same time Fig. 4 is an enlarged section taken on the line 4-4 of Fig. 1.

Fig. 5 is an enlarged cross section taken on the line 5--5 of Fig. 1.

Fig. 6 is a cross section of the peripheral rim of the propeller and showing a reinforcement therefor.

Referring by numerals to the accompanying drawing which illustrates a preferred embodiment of my invention, I0 designates a hub, with which is formed integral, the inner ends of a plurality of radial blades II which are correspondingly inclined in cross section, also inclined lengthwise so that their outer ends occupy a plane rearwardly of their inner ends and the hub.

Thus the propeller is substantially dish shape,

lined effect.

the outer ends of the blades which are inclined, and the inclined plates I8, will force air through openings I5 and I! in the rim so as to produce a tubular column of air surrounding th column driven rearwardly by the inner portions of the blades, thus producing a high degree of pulling or lifting force upon the aircraft with which the propeller is associated.

To reinforce the rim portion of the propeller and provide resistance to bursting strains developed while said propeller is rotated at high speeds, a member, preferably a steel cable such as C, may be embedded in the rim member I2 (see also in rotary pumps, compressors, impellers and the like.

Thus it will be seen that I have provided a propeller which is simple in structure, inexpensive of 3 manufacture and very ffective in performing the functions for which it is intended.

It will be understood that minor changes in the size, form and. construction of my improved propeller may be made and substituted for those herein shown and described without departing from the spirit of my invention, th scope of which isset'forth in the appended-claims tion, a peripheral ring integrally connected to the outer ends of said blades, which ring is lozenge shape in cross ection and being ofiset rearwardly from said hub, a continuous flange projecting inwardly from said ring between its front and rear ends, the inner edge of which flange is secured to said blades inwardly from their ends, and there being spaced openings formed in said n ea *2. An airplane propeller as set forth'in claim 1, with inclined plates integral with said flange in WILLIAM I. JACKSON. 

